Bombload handling apparatus

ABSTRACT

Subject disclosure relates to novel and improved apparatus for loading and unloading a bombload ejection subassembly on an aircraft bombrack. When an asymmetric bombload is to be handled, the apparatus includes a sheave assembly which is secured to the bombload assembly such that its axis of rotation is positioned vertically above the center of gravity of the bombload assembly, a single cantilever element which hooks or locks on the aircraft bombrack frame and extends outwardly over the sheave assembly and a hoist mechanism which is cradled on the end of the cantilever element and controls a lifting cable which is reeved about the sheave assembly. When a symmetric bombload is to be handled, the apparatus includes a pair of sheave assemblies which extend outwardly from opposite sides of the bombload assembly, a pair of cantilever elements which are secured to the bombrack frame above the sheave assemblies, and a hoist mechanism.

United States Patent Ruggeri [54] BOMBLOAD HANDLING APPARATUS Joseph P. Ruggeri, 214 Third Ave., Cherry Hill, NJ. 08034 [22] Filed: Jan. 14, 1971 [21] Appl.No.: 106,520

[72] Inventor:

Primary Examiner-Edward A. Sroka Attorney-R. S. Sciascia and A. W. Collins 451 Apr. 4, 1972 s71 ABSTRACT Subject disclosure relates to novel and improved apparatus for loading and unloading a bombload ejection subassembly on an aircraft bombrack. When an asymmetric bombload is to be handled, the apparatus includes a sheave assembly which is secured to the bombload assembly such that its axis of rotation is positioned vertically above the center of gravity of the bombload assembly, a single cantilever element which hooks or locks on the aircraft bombrack frame and extends outwardly over the sheave assembly and a hoist mechanism which is cradled on the end of the cantilever element and controls a lifting cable which is reeved about the sheave assembly. When a symmetric bombload is to be handled, the apparatus includes a pair of sheave assemblies which extend outwardly from opposite sides of the bombload assembly, a pair of cantilever elements which are secured to the bombrack frame above the sheave assemblies, and a hoist mechanism.

7 Claims, 3 Drawing Figures PATENTEDAPR 41972 3,658,614

sum 1 or 2 INVI'JN'I'OR.

JOSEPH P. RUGGERI QJLLQJL,

ATTORNEY PATENTEDAPR 4 I972 sum 2 OF 2 INVENI'OR.

JOSEPH P. RUGGERI Mk. W

ATTORNEY BOMBLOAD HANDLING APPARATUS The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor. I

Various types of handling apparatus has been devised and used in the past to load and unload bombloads on military aircraft. Considerable difficulty. has been experienced heretofore, however, in providing apparatus of this kind which satisfies the requirements of the operation in a practical and effective manner.

It is therefore a principal object of the invention to provide novel and improved apparatus for loading and unloading a bombload on an aircraft.

It is a further object of the invention to provide novel and improved handling apparatus which maintains asymmetric as well as symmetric bombloads in a stable condition during loading and unloading operations.

It is therefore a further object of the invention to provide novel and improved bombload handling apparatus which requires the use of only one hoist mechanism.

It is a further object of the invention to provide novel and improved bombload handling apparatus which doubles the mechanical advantage of the hoist mechanism used, thereby permitting the use of one 2,000 pound capacity hoist in raising 4,000 pound loads.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawing wherein:

FIG. 1 is an end view partly in section of a preferred embodiment of the invention where a symmetrical bombload is being loaded on an aircraft;

FIG. 2 is an end view partly in section of a preferred embodiment of the invention where an asymmetrical bombload is being loaded on an aircraft; and

FIG. 3 is an enlarged cross-sectional view of a preferred embodiment of a bombrack to which a bombload assembly may be secured by means of the improved apparatus of the invention.

Referring now to the various figures of the drawing, it will be noted that the bombload ejector rack 3 is suspended from the lower surface of the wing or fuselage 5 of the aircraft in any suitable manner. The bombload ejector rack 3 includes the elongated structural frame or housing 7 which is generally rectangular in cross-section, two or more bombload suspension hooks 9 positioned in recesses in the bottom of the frame 7, an ejector mechanism 11 which controls operation of the suspension hooks 9 between open and closed positions and two or more pairs of adjustable sway braces 13. Inasmuch as the structural and operative details of the identified and other components of the bombload ejector rack 3 by themselves form no part of the present invention, a full description of the same is not included herein for the sake of simplicity. For a full understanding of the invention, it need only be understood that for release and ejection of the entire bombload assembly 15, a suitable mechanical or electrical impulse is employed to energize the ejector mechanism 11, operate the suspension hooks 9 to their open position and release the bombload assembly from the rack 3. The conventional adjustable sway braces 13 engage the exterior surface of the bombload assembly l5 and limit its pitching and yawing movement on the suspension hooks 9.

The bombload assembly 15 includes a hexagonal structural frame member 17, two or more suspension lugs 19 that are adapted to engage the suspension hooks 9 on the bombload ejector rack 3, and one or more individual bomb accommodation and ejection units 21. Each bomb accommodation and ejection unit 21 includes a frame or housing 23, one or more bomb suspension hooks 25, an ejector mechanism 27 which controls operation of the suspension hooks between open and closed positions and two or more pairs of adjustable sway braces 29. Again, inasmuch as the structural and operative details of the identified and other components of the bombload assembly 15 by themselves form no part of the invention, a full description of the same are not included herein for the sake of simplicity. For a full understanding of the invention, it need only be understood that for release and ejection of any individual bomb 31 of the bombload assembly 15, a suitable mechanical or electrical impulse is employed to energize the associated ejector mechanism 27, disengage the associated suspension hooks 25 from the lugs 33 on the bomb 31 and eject the bomb 31. The conventional adjustable sway braces 29 engage the exterior surface of the bomb 31 prior to its ejection and limit its pitching and yawing movement on the suspension books 25.

The sheave assemblies 35 and 37 may be secured in any suitable conventional manner to the hexagonal frame member 17 of the bombload assembly 15 such that they project outwardly from either or both sides thereof. Each sheave assembly includes a sheave 35a or.37a which is joumaled on an axis which lies vertically above the center of gravity of the bombload assembly 15 when the same is asymmetrically loaded as shown in FIG. 2 of the drawing.

As shown in FIGS. 1 and 2 of the drawing, the cantilever bombload hoist adapter elements 39 and 41 may be hooked or securely positioned on the frame or housing 7 of the bombload ejector rack 3 such that they project outwardly from either or both sides thereof. The upper portion of one end of each cantilever element includes a hook-shaped projection 39a or 41a which is designed such that in its locked position on the ejector rack 3, the inner surface of the end of the projection 390 or 41a engages one side of the ejector rack frame 7 and the lower portion of the end of the element 39 or 41 engages the other side of the ejector rack frame 7. The lower portion of the other end of each cantilever element 39 or 41 includes a bifurcated hookshaped projection 39b or 41b.

It is to be understood that although the dovetailed ends 39a or 41a of the cantilever elements are preferably designed as described herein to engage the frame 7 and support a load on a rack which is generally rectangular in cross-section, any other suitable design of the cantilever element could be used to engage a similar or other type of rack frame without departing from the spirit or scope of the invention.

The hoist 43 is of conventional design and preferably includes a gas powered cable storage and payout reel not shown in the drawing, an elongated tubular arm 43a, a sheave 43b joumaled on the end of arm 43a and a cable 43c. The bifurcated hook-shaped projection 39b or 41b of the cantilever element 39 or 41 is designed to cradle the trunnioned ends of the shaft 43d on which the sheave 43b of hoist 43 rotates such that the hoist 43 is supported thereby and extends downwardly and outwardly from the bombload assembly 15. When a symmetrical bombload is to be secured on the aircraft as indicated in FIG. 1 of the drawing, the cable 43c of hoist 43 extends from the hoist storage and payout reel, through its tubular arm 43a, about the sheave 43b, about the sheave 35a on one side of the bombload assembly 15, about the sheave 37a on the other side of the bombload assembly 15 to a suitable pin element or the like 45 which when secured in the aperture 47 in the cantilever element 41 provides a suitable anchor for the end of cable 430. When an asymmetrical bombload is to be secured on the aircraft, as indicated in FIG. 2 of the drawing, the cable 43c extends from the storage and payout reel of the hoist 43, through the tubular arm 43a, about the sheave 43b, about the sheave 35a on the bombload assembly 15 to the pin element 49 which is secured in the aperture 51 in the cantilever element 39.

In operation, when a symmetrical load is to be secured on the aircraft as in FIG. 1 of the drawing, the bombload assembly 15 is positioned beneath the aircraft wing or fuselage 5 such that the upwardly directed lugs 19 are vertically aligned with the suspension hooks 9 on the ejector rack 3. The sheave assemblies 35 and 37 are then secured to the bombload assembly 15 such that they extend outwardly from opposite sides thereof. The cantilever elements 39 and 41 are then positioned on the frame of the ejection rack 3 such that they extend outwardly from opposite sides of the frame. The hoist 43 is then positioned and cradled on the bifurcated hook-shaped projection of one cantilever element 39. The cable 430 of the hoist is then reeved from the hoist sheave 43b about the sheaves 35a and 37a on the bombload assembly 15 to the anchoring pin 45 in aperture 47 of cantilever element 41. The hoist 43 is then energized so that cable 430 is retracted and the bombload assembly 15 is lifted upwardly toward the rack 3 on the aircraft. When the lugs 19 on the bombload assembly are fully inserted in the recesses in the ejection rack 3, the ejector mechanism 11 is energized and the suspension hooks 9 are operated to their closed position where they engage lugs 19 and secure the bombload assembly on the aircraft. The cantilever element anchor pin 45 is then removed, cable 43c is withdrawn from sheaves 35a and 37a and the hoist 43 is removed from cantilever element 39. The cantilever elements 39 and 41 are then removed from the frame of the rack 3, the sheave assemblies 39 and 41 are removed from the bombload assembly 15 and the bomb load on the aircraft is ready for flight.

Removal of the bombload assembly 15 from the aircraft is accomplished by reversing the described bomb loading procedure.

When an asymmetrical load is to be secured on the aircraft as in FIG. 2 of the drawing, again the bombload assembly 15 is positioned beneath the aircraft wing or fuselage such that the lugs 19 are vertically aligned with the suspension hooks 9 on the rack 3. The sheave assembly 35 is then secured to the bombload assembly such that it extends outwardly from the side of the assembly 15 that is more heavily loaded. The cantilever element 39 is then positioned on the frame 3 such that it extends outwardly above the sheave assembly 35. The hoist 43 is then positioned and cradled on the bifurcated hook-shaped extremity of cantilever element 39. The cable 43c of the hoist is then reeved from the hoist sheave 43b about the sheave 35a on the bombload assembly to the anchoring pin 49 in aperture 51 in cantilever element 39. The hoist is then energized so that cable 430 is retracted and the bombload assembly is lifted on its center of gravity upwardly toward the rack 3 on the aircraft. When the lugs 19 of the bombload assembly are fully inserted in the recesses in the rack 3, the ejector mechanism 11 is energized and the suspension hooks 9 are operated to their closed position where they engage lugs 19 and secure the bombload assembly on the aircraft. The cantilever element anchor pin 49 is then removed from the frame of the rack 3, the sheave assembly 35 is removed from the bombload assembly 15 and the bomb load on the aircraft is ready for flight.

Removal of the bombload assembly 15 from the aircraft is accomplished by reversing the described bomb loading procedure.

Obviously, many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims, the invention may be practiced otherwise than as specifically described.

What is claimed is:

1. Apparatus for loading and unloading a bombload assembly on an aircraft bombrack, said apparatus comprising:

a. a first cantilever element which hooks and locks on the aircraft bombrack and extends outwardly from one side thereof;

b. a first sheave which is rotatably mounted on the bombload assembly;

0. a cable hoist which is connected to the cantilever element and extends downwardly and outwardly therefrom;

d. and a cable which is affixed at one end to the cantilever element and extends downwardly around the first sheave and upwardly to the hoist.

2. The apparatus substantially as described in claim 1 wherein the bombload assembly is not symmetrically loaded and the extended center of gravity of the bombload assembly passes upwardly through the axis of the first sheave and the outwardly extended cantilever element.

The apparatus substantially as described In claim 1 wherein the bombrack is generally rectangular in cross-section and wherein the upper portion of the end of the cantilever element which locks on the bombrack includes a hook-shaped projection such that when the cantilever element is locked on the bombrack, the inner surface of the hook-shaped projection engages one side of the bombrack and the lower portion of the said end of the cantilever element engages the other side of the bombrack.

4. The apparatus substantially as described in claim 1 and further comprising:

a. a second cantilever element which locks on the aircraft bombrack and extends outwardly from the other side thereof; and

b. a second sheave which is rotatably mounted on the bombload assembly, said first and second sheaves being mounted on opposite sides of the bombload assembly, and said cable extending from a fixed point on the second cantilever element downwardly around the first and second sheaves and upwardly to the hoist.

5. The apparatus substantially as described in claim 4 wherein the bombload assembly is symmetrically loaded.

6. The apparatus substantially as described in claim 4 wherein the bombrack is generally rectangular in cross-section and wherein the upper portion of the end of each cantil ever element that locks on the bombrack includes a hookshaped projection such that when the cantilever elements are locked on the bombrack, the inner surface of the hook-shaped projection of each cantilever element engages one side of the bombrack and the lower portion of the end of each cantilever element engages the other side of the bombrack.

7. The apparatus substantially as described in claim 1 wherein the hoist is a gasoline powered device. 

1. Apparatus for loading and unloading a bombload assembly on an aircraft bombrack, said apparatus comprising: a. a first cantilever element which hooks and locks on the aircraft bombrack and extends outwardly from one side thereof; b. a first sheave which is rotatably mounted on the bombload assembly; c. a cable hoist which is connected to the cantilever element and extends downwardly and outwardly therefrom; d. and a cable which is affixed at one end to the cantilever element and extends downwardly around the first sheave and upwardly to the hoist.
 2. The apparatus substantially as described in claim 1 wherein the bombload assembly is not symmetrically loaded and the extended center of gravity of the bombload assembly passes upwardly through the axis of the first sheave and the outwardly extended cantilever element.
 3. The apparatus substantially as described in claim 1 wherein the bombrack is generally rectangular in cross-section and wherein the upper portion of the end of the cantilever element which locks on the bombrack includes a hook-shaped projection such that when the cantilever element is locked on the bombrack, the inner surface of the hook-shaped projection engages one side of the bombrack and the lower portion of the said end of the cantilever element engages the other side of the bombrack.
 4. The apparatus substantially as described in claim 1 and further comprising: a. a second cantilever element which locks on the aircraft bombrack and extends outwardly from the other side thereof; and b. a second sheave which is rotatably mounted on the bombload assembly, said first and second sheaves being mounted on opposite sides of the bombload assembly, and said cable extending from a fixed point on the second cantilever element downwardly around the first and second sheaves and upwardly to the hoist.
 5. The apparatus substantially as described in claim 4 wherein the bombload assembly is symmetrically loaded.
 6. The apparatus substantially as described in claim 4 wherein the bombrack is generally rectangular in cross-section and wherein the upper portion of the end of each cantilever element that locks on the bombrack includes a hook-shaped projection such that when the cantilever elements are locked on the bombrack, the inner surface of the hook-shaped projection of each cantilever element engages one side of the bombrack and the lower portion of the end of each cantilever element engages the other side of the bombrack.
 7. The apparatus substantially as described in claim 1 wherein the hoist is a gasoline powered device. 